XFOIL         Version 6.94
  
 Calculated polar for: SIKORSKY DBLN-526 AIRFOIL                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.080     Re =     0.300 e 6     Ncrit =   9.000
  
  alpha     CL        CD       CDp       CM    Top_Xtr Bot_Xtr
 ------- -------- --------- --------- -------- ------- -------
   0.000   0.3100   0.03072   0.02504  -0.0805  0.8122  0.9051
   0.500   0.4094   0.02873   0.02295  -0.0907  0.8166  0.9162
   1.000   0.5027   0.02745   0.02160  -0.0999  0.8184  0.9294
   2.000   0.5826   0.02995   0.02412  -0.0957  0.8004  0.9534
   2.500   0.6707   0.02893   0.02305  -0.1042  0.7994  0.9623
   3.000   0.7743   0.02738   0.02148  -0.1163  0.7982  0.9685
   4.500   0.9958   0.02724   0.02143  -0.1336  0.7761  0.9902
   5.000   1.0254   0.02875   0.02303  -0.1295  0.7615  0.9948
   5.500   1.1489   0.02623   0.02045  -0.1460  0.7518  0.9972
   6.000   1.1851   0.02722   0.02155  -0.1432  0.7345  0.9993
   6.500   1.2338   0.02683   0.02116  -0.1429  0.7182  1.0000
   7.000   1.2345   0.02703   0.02115  -0.1311  0.6766  1.0000
   7.500   1.2360   0.02801   0.02212  -0.1205  0.6499  1.0000
   8.000   1.2375   0.02924   0.02335  -0.1102  0.6199  1.0000
   8.500   1.2495   0.03035   0.02428  -0.1023  0.5818  1.0000
   9.500   1.2821   0.03353   0.02712  -0.0896  0.5184  1.0000
  10.000   1.3050   0.03540   0.02895  -0.0852  0.4942  1.0000
  10.500   1.3309   0.03751   0.03115  -0.0817  0.4722  1.0000
  11.000   1.3287   0.04181   0.03525  -0.0736  0.4056  1.0000